Aeroplane



Juy 5,' 1932.

. y E. H. LANIER.

AEROPLANE Filed NOV. 16, 1931 4 Sheets-Sheet 1 July 5, 1932.. Y E. H. LANn-:R 1,866,214

' AEROPLANE I Filed Nov. les, 1951 4 sheets-sheet 2 dttouwq `Iuly 5, 1932. E. H. LANIER AEROPLANE Filed NV. 16 1931 4 sheets-sheet 3 gva/wanton mwa/41 Paten-ted `luly 5, 1932 PATENT OFFICE EDWARD H. LANIER, OF MIAMI, FLORIDA AEROPLANE Application ala November 1e, 1931. semi no. 575,342.

My present invention relates to the art of aerial navigation 4and particularly to aeroplanes of the kind disclosed in my Letters Patents 1,750,529 vissued March 11, 1930, 5 1,779,005 issued October 21, 1930, 1,803,805 iss'ued May 5, 1931, and 1,813,627 issued July Primarily my present invention has for its objects to produce an aeroplane having a high degree of inherent stability, bringing closer the ratio of plane to pilot for added safety; to provide one which needs less space for maneuvering, less hangar room, one which can carry more useful load and has less production cost than the aeroplanes now commonly employed.

Further, it is an object to provide for the concentration of the lift close in to the center.

of gravity, the concentrated directional forces merging in a common point over a low center of gravity to produce a high degree of automatic stability or balance.

Further, it is an object to provide an aeroplane in which the air foil may be a conventional stream lined wing curve with sli ht modifications, dihedral in form on the un erside and air-tight with the exception of an opening in the top surface to evacuate the air and produce low pressure within the airfoil (hereinafter termed cellule), creating relatively more lift than the conventional wing in one-half the span and thus concentrating the lifting forces close in to the center of gravity. Other objects will in part be obvious and in part be pointed out hereinafter.

To the attainment ofthe aforesaid objects and ends, the invention still further resides in the novel details of construction, combination and arrangement of parts, allof 'which will be first fully described in the following detailed description, then be particularly pointed out in the appended claims', reference ein had to the accompanying drawings, in Whi 2` Figure 1 is a perspective view of my present aeroplane.

Figure 2 is a rear perspective view of the i Same.

Figure 4 is a central vertical longitudinal section of the same.

Figure 5 is a plan view of a modification of the invention.

Figure 6 is a plan view of another modi- 55' cation.

Figure 7 is a diagrammatic cross section illustrating the action of the air pressures, etc. in 'planes having a narrowopening in the top.

Figure 8 is a diagrammatic cross section illustrating the action of the air pressures, etc. in planes having wide openings in the top.

Figure 9 is a perspective view of a conven- 65 zional aeroplane equipped with my inven- In4 the drawings in which like numerals of reference indicate like parts in all of the iigures, 1 represents the body proper of the aero- 70 plane which may be of any approved -construction, 2 indicates the front landing gear, 3 the tail skid, 4 the usual rudders and elevators and 5 the usual motor driven ropeller. Extending upwardly from the ody 1 is a vertical iin-like structure 6 which can be a part of the cabin in cabin type planes if desired. This structure serves to connect the body with the airfoil. The vertical lin-like structure 6 is provided with an open chamber at the front, the forepart of which carries a transparent windshield 7 while the rear portion 8 may be used toenclose a vacuum chamber or pocket 20 that is in communica- 85 tion solely with the interior of the airfoil.

The bow of the fin-like structure 6 is curved upwardly and forwardly as at 9 while the stern is curved downwardly and rearwardly as at 10.` 9

The airfoil preferably consists of a central .level (approximately horizontal) part 11Y from which extend laterally upwardly intermediate parts 12 that terminate in tip parts 13,- the latter extending approximately parallel to the central part 11. Ailerons 14: are provided on `the laterally extended ends 13 of the airfoil and operated in the usual way.

The extreme lateral parts of the airfoil are 10o preferably provided with tip boards 15 to prevent tip loss` and tip dra The airfoil consists of aollow or chambered body composed of a suitable framing and an air-tight envelope covering, the covering being intact on the lower surface ofthe airfoil but having an opening 16 in the top surface through which the air may be sucked from within the `airfoil to evacuate its chamber.

18 designates the top covered part of the.

intermediateA lateral extensions 12 of the airfoil while 19 indicates the top covering of the laterally extended ends or tips 13.

In the embodiment of the invention shown in Figure 9, which is a conventional type-1 aeroplane consisting ofthe cabin 21 having the observation room 22 for the pilot andV controls and having the conventional wing 23, I modify the construction by making the envelope of the wing of an air-tight covering and providing a transverse open slot 24 in the top as shown.

In Figures 7 and 8 I have indicated diagrammatically the direction of forces acting to lift the aeroplane. 7 Inathose figures A indicates the bottom surfaces of the intermediate portions of the airfoil whose ratio of lift approximates thirty-three and one-third percent (the same as with conventional wings). B indicates vthe insideskin of the airfoil whose ratio of liftapproximates sixty-six land two-thirds percent (in the conventional wing its ratio is zero). C. indicates the top surface -of the airfoil whose ratio of lift approximates sixty-six and twothirds percent, the same as with conventionalwings.

From these diagrammatic figures it will be `observed that there is provided a higher degre of vacuum suction force within the airfoil; more eiiiciency, relatively, in the lift of the surfaceI B as a whole; and more square feet exposed to lift surface B; and the open top area D allows suction to act on lower surface B, thereby increasing lower eiliciency C: cab

to one hundred ercent.

While in the rst five figures of the drawings I have shown the fin-like structure 6' 'as provided with a rear chamber 8 in com- Octagon shape in top plan, it could be made in other forms as for example with a round outside diameter in the form of a disc, but as the geometric form Iis not material to the invention I do not wish to be understood-as' being limited to any particular form, be it oc-l theair and produce lower pressure within the airfoil.Y y l By reference especially to the diagrammatlc Figures 7 and 8, it will be noted that the suction forces that normally acted on the vtopjsurface C takes action on the lower sur- ;face-B due to the fact that the opening D `brings'them in direct contact with the rareficationby suction. This brings efficiency of the lower surface B up, due to the fact that in the normal wing the suction lift is exposed to the upper skin C of the wing only. It will be. readily seen that the action of this force adds lift to the lower surface A over and above the pressure forces utilized in the 0rdinary section.

As vacuums and pressures distribute an equal poundage over every square inch of surface of a retainer, it will be readily seen that the much larger exposure that can be obtained in the cellule, gives a greater force value than can be obtained by the utilization of the upper surface C only, and when the exhaustion or rareiication in proportion to the speed has taken place, the panel in its entirety conforms tothe performance of the 'normal wing in regard to the top surface exposed.

' The vents in the top surface of the airfoil should be located over the center of lift and about one-third distance back of the entering edge in order to localize the center ofpressure in a moderate range over the center of gravity. The vents can be a lateral slot or slots, round or oval hole or holes, Whichever should prove the most eiicient in practice.

In motion the suction lift forces on the inside bottom skin of the airfoil passing through the vents merge or concentrate directly over the center of lift (see Figure 8). Due to the narrow span of. the airfoil the lift is concentrated close in and over the center of gravity producing inherent stability of a high degree, insuring maneuverability, bringing closer the ratio of plane and pilot, requiring less hangar space and being much cheaper and lighter to build than the conventional wing. Built up spars and ribs in the airfoil are not necessary but may be used if desired.

Structurally the airfoil can be built in three sections, the middle or center section, a part of the fuselage, and the two outer sections bolted or hinged to the center section, folding down, or the airfoil can be built independently of the fuselage. Such details of manufacture are within the mechanical ability of aeroplane engineers and therefore illustration of the same in this application is thought to be unnecessary.

It is important, however, that the fuselage and airfoil be connected longitudinally by a partition to prevent side slip, such a partition as for instance the vertical lin-like structure 6.

The theory of gettin additional lift from. a given area is applicab e to the conventional wing of today with few changes, simply by making the Wing air-tight and supplying vents or openings in the top surface to evacuate the air, t-hus increasing the pay load without an increase in structural weight (see Figure 9). Lift is also exerted on the inside bottom skin of the 'airfoil above the`- cabin which, on the conventional wing, is lnegligible. On planes with large cabins this additional lift would greatly increase payload. From the foregoing description, taken in connection with the accompanying drawings, it is thought the complete construction, operation and advantages of my invention will be clear to those skilled in the, art to which it relates. e

What I claim is:

l. In an aeroplane, a body having suitable landing gear, a rudder and an elevator, an airfoil mounted over the body and comprising a hollow wing-like structure composed of a central section having its under surface horizontal, a pair kof intermediate portions extending laterally from said central portion and having their under surfaces inclined upwardly laterally from the under surface o the central portion, and a pair of tip portions extending laterally from said intermediate portions with the under surfaces of said tip portions approximately horizontal, said tip portions having their top surfaces and bottom surfaces intact, said central portion having an air evacuation opening in its top surface, substantially as and for t e purposes described.

2. In an aeroplane, a body having suitable landing gear, a rudder and an elevator, an airfoil mounted over the body and comprising a hollow wing-like structure composed of a central section having its under surface horizontal, a pair of intermediate portions extending laterallyA from said centralportion -and having their under surfaces inclined upwardly laterally from the under surface of the central ortion, and a pair of tip portions exten ing 'laterally from said intermediate portions with the under surfaces of said tip portions approximately horizontal, said tip portions having their top surfaces and bottom surfaces intact, said intermediate and said central portions having together an opening in their top surfaces. x

3. In an aeroplane, a bod having sultable landing gear, a rudder an an elevator, an

upwardly laterally from the under surface of thecentral portion, and a pair of tip portions extending laterally from said intermediate portions with the under surfaces of said tip portions approximately horizontal, said tip portions having their top surfaces and bottom surfaces intact, said central portion having an air evacuatlon opening in its top surface, and a fin-like structure connecting said airfoil with said body.

. 4. In an aeroplane, a body having suitable landingV gear, a rudder and an elevator, an airfoil mounted over the body andl comprising a hollowv wing-like structure composed of a central section having its under surface horizontal, a pair of intermediate portions extending laterally from said central portion and having their under surfacesl inclined upwardly laterally from tlieunder surface of the central portion, and a p'air of tip portions 'extending laterally from said intermediate portions with the under surfaces of said tip vportions approximately horizontal, said tip tending laterally from said central portion and having their under surfaces inclined upwardly laterally from the under surface of the central portion,.and a pair of tip portions extending laterally from said intermediate portions with the under surfaces of said tip portions approximately horizontal, said tip portions having their top-surfaces and bottom surfaces intact, said central portion having an air evacuation opening in its top surface, and a iin-like structure connecting said airfoil with said body and itself including a chamber in communication only with the interior of said airfoil for the purposes described.

6. In an aeroplane, a body having suitable landing gear, a rudder and an elevator, an airfoil mounted over the body and comprising a hollow wing-like structure composed of `a central section having its under surface horizontal, a pair of intermediate portions wardlyglaterally from the under surface of' 'l the central portion, and a pair of tip portions extending laterally from said intermediate portions with the under surfaces of said tip portions approximately horizontal, said Atip portions having their top surfaces and bottom surfaces intact, said intermediate and said central portions having together an opening in their top surfaces, and a fin-like structure connecting said airfoil with said body, and itself including a chamber in communication only with the interior of said airfol for the purposes described. 7 In an aeroplane, a body having suitabl landing gear, a rudder'and an elevator, an

airfoil mounted over the body and comprisv y ing a hollow Wingflike-structure composed of a central section having its under surface;

horizontal, a pair of intermediate portions .extending laterally from said central portion l and having their under surfaces inclined upwardly laterally from the .under surface of the central portion, and a pair of tip portions extending laterally from saidintermediate portions with the under surfaces of said tip portions approximately horizontal, said tip portions having their top surfaces and bottom surfaces intact, said central portion having an air evacuation opening in its top surface, and tip boards at the lateral extremities of said airfoil.

EDWARD H; LANIER. 

